A Method for Deployble Structures With Linear Springs

摘要

In order to use the payload of the rocket fully and enhance the functions of the satellite's components at the same time, it is necessary to construct solar battery arrays and large scale antennas with deployable structure. In deployable structure springs are often used. The character of the spring joint in the deployable structure is not like that of hinge joint and rigid coupling, so it is not convenient to analyze structures with springs by conventional FEM programs. In this article the substructure mechanical model of a type of deployable structure is built at the beginning, then the method of reducing degress of freedom is employed to deduce the stiff formulation of spatial beam element with linear twisting spring. Also an analysis of this type ofdeployable structure is made. The example shows that this method is effective.